In general, there is a mismatch between a finite element model {(FEM)} of a structure and its real behaviour. In aeronautics, this mismatch must be small because {FEM}s are a fundamental part of the development of an aircraft and of increasing importance with the trend to more flexible wings in modern designs. Iterative finite element model updating can be computationally expensive for complex structures, and surrogate models can be employed to reduce the computational burden. A novel approach for FEM updating, namely assembly-like, is proposed and validated using real experimental data from a flexible wing. The assembly-like model updating framework implies that the model is updated as parts are assembled. Benchmarking against the classical global, or one-shot, approach demonstrates that the proposed method is more computationally efficient, since a normalised workload proxy based on solver-reported model size and memory footprint indicates about 28\% lower overall effort. Aapproximately 95\% of the required solves are performed on lower-fidelity subassembly models with smaller equation counts and memory requirements. Despite the reduced reliance on full-wing evaluations, the new approach retains the fidelity, within 1\% of a joint natural frequencies and modal shapes index, of the global approach.

翻译：通常，结构的有限元模型与其真实行为之间存在偏差。在航空领域，这种偏差必须很小，因为有限元模型是飞行器开发的基础部分，并且随着现代设计中更柔性机翼的趋势而日益重要。对于复杂结构，迭代式有限元模型更新在计算上可能代价高昂，而代理模型可用于降低计算负担。本文提出了一种新颖的有限元模型更新方法——即“组装式”方法，并使用柔性机翼的真实实验数据进行了验证。该组装式模型更新框架意味着模型随着部件组装而被更新。与经典的全局（或称一次性）方法相比，基准测试表明，所提出的方法在计算上更高效，因为基于求解器报告的模型规模和内存占用的标准化工作量代理指标显示，总体工作量降低了约28%。大约95%所需的求解操作是在方程数量和内存需求较小的低保真度子组件模型上执行的。尽管减少了对全机翼评估的依赖，新方法仍保留了保真度，其联合固有频率和模态形状指标与全局方法的偏差在1%以内。